EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April From MOP to MTG MTG MSG MOP UVS coordinated with GMES Sentinel 4 5 observation missions: - HRFI: 5 channels - FDHSI: 22 channels - Lightning Imager - Infra-Red Sounder -3-axis stabilised satellite(s) 1 observation mission: -MVIRI: 3 channels -Spinning satellite 2 observation missions: - SEVIRI: 12 channels - GERB - Spinning satellite

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April From MOP to MTG 10 x 100 x 2 x 8 x 4 x MVIRI SEVIRI HRFI FDHSI IRS LI MTG Mission Objectives: Ambitions in line with expected future space systems evolution A quantum leap forward requiring significant development and programmatic efforts compared to the previous Meteosat systems Payload Budgets Evolution (Current Estimate)

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April MTG System Elements From MTG Mission needs to MTG System Elements

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April MTG Candidate Space Segment Concepts Instrument concepts derived from current observation mission needs require 3-axis stabilised platform. Heritage from 3-axis GEO telecom platforms not fully satisfactory for demanding EO missions Enhancements are needed MOP MSG MTG

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April MTG Candidate Space Segment Concepts Several space segment concepts considered during the trade off: 1. 4 satellites supporting one instrument each (would require up to 8 satellites - nominal + back-up - in orbit. Satellite launch mass not compatible with any low cost launcher) -> option discarded 2. 1 satellite supporting the full payload complement 3. 2 satellites supporting the payload complement Payload options: two separate imagers (HRFI+FDHSI) or single combined imager 1 2 3

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space Segment Concepts – Single Satellite Deployable Solar Array Launch Mass: ≈ 6000 kg Power: ≈ 2.6 kW Launchers: Ariane 5 (Atlas V5/ Delta 4) Raw Data Rate: > 350 Mbps Chemical Propulsion system Electric propulsion could be considered for station keeping and RW off-loading Body Mounted Solar Array Launch Mass: ≈ 7000 kg Power/raw data rate as per Deployable SA wing concept Reduced solar pressure torques No disturbances from solar array rotation Launch mass penalty of about 1 ton Critical configuration

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space Segment Concepts – Single Satellite Lifetime and mission availability requirements over 15 (+5) yrs require 2 (TBC) nominal satellites + 2 (TBC)hot back-up in orbit

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April A total of 8 imagers (4 HRFI + 4 FDHSI) would be required for the two imagers configuration A single combined imager fulfilling the HRFI/FDHSI mission need in a exclusive way will reduce the imagers complement by half and reduce the launch mass and complexity of the satellites, as well as possibly the launch cost. Estimated savings: % on space segment/launcher costs Space Segment Concepts – Single Satellite FDHSI HRFI IRS LI FDHSI HRFI IRS LI FDHSI HRFI IRS LI FDHSI HRFI IRS LI Operational Spare HRFI + FDHSI COMBINED IMAGER Operational Spare C-Imager IRS LI C-Imager IRS LI C-Imager IRS LI C-Imager IRS LI Launch Mass: ≈ 6 tons Power: ≈ 2.6 kW Launch Mass: ≈ 5 tons Power: ≈ 2.2 kW 8 imagers: 4 HRFI + 4 FHSI 4 Combined Imagers

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space Segment Concepts – Two Satellites FDHSI HRFI Star Trackers UHF antenna X-band antenna North or South Earth LI IRS North or South Earth UHF antenna Ka-band antenna Star Trackers IRS radiator sunshield Baseline Launcher: Soyuz Back-up: Proton K Two imagers (HRFI + FDHSI) configuration

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space Segment Concepts – Two Satellites LI Combined imager North or South Earth UHF antenna X-band antenna 400 N thruster IRS North or South Earth UHF antenna Ka-band antenna 400 N thruster IRS radiator sunshield Baseline Launcher: Soyuz Back-up: Proton K Combined imager configuration

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space Segment Concepts – Two Satellites Sat 1 Sat 2 Lifetime and mission availability requirements over 15 (+5) yrs require 4 (TBC) nominal satellites + 4 (TBC)hot back-up in orbit A total of 8 imagers (4 HRFI + 4 FDHSI) would be required for the two imagers configuration. A single combined imager fulfilling the HRFI/FDHSI mission needs in an exclusive way will reduce the imagers complement by half and reduce the launch mass and complexity of the satellites, as well as possibly the launch cost. Estimated savings: % on space segment/launcher costs

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space Segment Concepts – Mission Communication Raw data rate from observation payload in excess of 300 Mbps => A factor 100 growth compared to MSG Communication payload architecture and selection of downlink frequencies depend on selected space segment concepts and apportionment of observation payload to the platforms Drivers: InfraRed Sounding Mission data rate (>200 Mbps depending on instrument concept – dispersive vs. FTS – and level of on-board processing/compression techniques) Even considering high order modulation schemes improving the bandwidth efficiency, L band downlink capacity would be limited to Mbps => higher frequency bands (X, Ka, Ku) Atmospheric attenuation effects at high frequencies and impact on the link availability may require considering adaptive data rate solutions based on the priorities of mission data => impact on the overall operational availability

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Ground Segment and Data Dissemination The ground segment design is impacted by: High data volumes (100 X MSG) associated to near real time timeliness (=> processing) requirements Data dissemination services to full scale real time users (National Met services, regional processing centers), data volumes estimates in the order of 200 Mbps after lossless compression. Realistic implementation scenarios based on dedicated terrestrial communication infrastructures Data dissemination to local real time users (subset of full MTG data set) through commercial services and low cost user terminals requires the definition of realistic dissemination scenarios to bring the data rate down to reasonable figures (20-30 Mbps) compatible with commercial dissemination system capabilities at reasonable costs in the 2015 time frame.

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Ground Segment and Data Dissemination Ground Segment architecture elements Terrestrial multi Gbps network (GEANT 2004)

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Critical requirements and system drivers The need date for ensuring the continuity of the operational meteorological service in geostationary orbit with high availability is 2015 => short development time for the full mission System complexity significantly higher than MSG Observation payload concepts require development of new technologies (detectors, active coolers) to meet the performance requirements with high reliability and present different development risks Programmatic requirements advise a flexible system deployment strategy tailored to the observation mission priorities The mission availability required for an operational service with the specified availability will be challenging to achieve with a 3-axis stabilised platform (lessons learned from GOES, intrinsic concept limitation, limited heritage from previous Meteosat systems) System pointing accuracy and stability (from spatial resolution and geometric accuracy requirements), thermal control (active cooling, limitations due to 3-axis platform stabilisation) and data handling (high raw data rate and on-board processing) are the major drivers at satellite level

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Full payload complement accommodation on a single satellite is challenging in terms of: Overall platform configuration Availability of radiative surfaces Disturbances introduced by instruments (combined imager, infrared sounder) with different scanning laws impacting the satellite pointing performances Complexity of key subsystems (thermal control, AOCS, data handling, mission communication payload) AIT complexity and risks In addition: No flexible system deployment strategy Launch failure implies total mission loss Development risks (beside platform specific risks) driven by the most critical payload element, the IRS, which has lower priority than the imaging mission Space segment concept – single satellite

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Space segment concept – two satellites IRS Combined Imager LI Simplified satellite configuration, LI accommodation not critical Decoupling of the IRS (second mission priority but higher development and system level criticality, e.g. pointing stability, thermal control, data handling ) Flexible and phased development and deployment (as well as financial) strategies are possible, in accordance with the programmatic requirements and the observing mission priorities Design drivers on key subsystems are kept within reasonable levels Operational system complexity is adversely affected (2 operational + 2 stand-by satellites)

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Concept Selection The following concept is selected for detailed analysis: Implementation of the imaging mission through the combined imager 4 imagers instead of 8 Simpler satellite configuration, reduced launch mass Significant cost savings (space segment/launcher) Payload accommodation (Combined Imager, IRS, LI) on multiple satellites Flexible system deployment and development approach Decoupling of higher risk sounding mission from the higher priority imaging mission Reduced complexity of key platform subsystems IRS Combined Imager LI HRFIFDHSI Combined Imager

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Objectives and Guidelines - I Due to complexity and detailed definition of the observing mission requirements, the focus in the first part of the study has been given to: Mission Requirement Analysis Candidate Instrument Concept Definition For the second part (up to the Mission Architecture Review – MAR): Focus on system aspects and other elements of the mission architecture Consolidation of instrument concepts Definition of interface requirements Identification of critical technologies Consolidation of system performance, operability and availability as required by the operational nature of the system

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Objectives and Guidelines - II Preliminary assessment of system complexity and critical technologies: Mission requirement can only be fulfilled with the implementation of the observation payload on 3-axis stabilised platform Limited heritage from previous generation of Meteosat Systems Critical Technologies detectors, active coolers (actions initiated) Platform thermo-elastic stability, micro-vibrations, AOCS, thermal control Operational deployment of the complete MTG system with the current mission objectives by 2015 is judged extremely critical, alternative deployment strategies will be studied Activities in the frame of the second part of the study shall include the evaluation of simpler mission concepts aimed at ensuring the continuity of the MSG imaging mission (with enhanced requirements) by 2015 with reasonable development and programmatic risks

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Conclusion - I The two MTG system studies at pre-phase A level are progressing according to schedule Mid-Term Review completed in March 2005 Objectives for the first part of the study have been achieved: Definition of candidate payload and system concepts Simplified concepts at payload level (combined imager) and risk reduction at system level (multiple satellite concepts) proposed and selected for detailed analysis in the second part of the study

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, April Conclusion - II Full MTG System deployment by 2015 will require significant development and financial efforts Phased system development and deployment approach in compliance with the MTG mission priorities will mitigate risks while satisfying the user requirements Further focusing on simplified mission concepts to ensure continuity of the imaging mission in the Post-MSG era (2015) with reduced development risks and affordable programmatic constraints Identified options shall be analysed in details at pre-feasibility level in the second part of the study (concept consolidation and preliminary design, performance evaluation, ROM cost estimates and required technology developments) Study results and parallel evolution of programmatic and financial requirements/constraints will allow EUMETSAT and ESA to select at the Mission Definition Review (MDR) the most appropriate mission concepts to be analysed at feasibility level in the Phase A system studies ( )